CN113339323A - Gas compressor inlet guide vane structure with brush seal - Google Patents
Gas compressor inlet guide vane structure with brush seal Download PDFInfo
- Publication number
- CN113339323A CN113339323A CN202110771396.XA CN202110771396A CN113339323A CN 113339323 A CN113339323 A CN 113339323A CN 202110771396 A CN202110771396 A CN 202110771396A CN 113339323 A CN113339323 A CN 113339323A
- Authority
- CN
- China
- Prior art keywords
- guide vane
- brush
- inlet guide
- casing
- seal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000007787 solid Substances 0.000 claims description 3
- 230000008676 import Effects 0.000 claims description 2
- 238000007789 sealing Methods 0.000 abstract description 10
- 238000000034 method Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/56—Brush seals
Abstract
The invention discloses a gas compressor inlet guide vane structure with brush type seal, which comprises a gas compressor inlet guide vane and a seal structure, wherein the seal structure is arranged on the gas compressor inlet guide vane, the seal structure comprises brush wires, a fixing ring and a fixing plate, the brush wires are arranged in the fixing ring, and the fixing ring is fixed with a casing through the fixing plate. The inlet guide vane structure of the compressor, which is designed by the invention, has the advantages that the brush type sealing structure is additionally arranged at the gap between the guide vane and the casing, so that the flow control of the guide vane to an inlet is more accurate, the leakage can be effectively reduced, the inlet airflow is more uniform, and the influence of the leakage flow of the gap at the top of the inlet guide vane on a main flow is reduced, thereby improving the efficiency of the compressor and even the overall efficiency of an engine.
Description
Technical Field
The invention relates to the field of impeller machinery, in particular to a gas compressor inlet guide vane structure with brush type seal.
Background
Various gas compressors are subjected to changes of climate and working conditions during operation, and the flow rate and the gas inlet angle of gas are often required to be adjusted. However, in the operation process, the blade top clearance of the inlet guide vane affects a flow field to reduce the efficiency of the compressor, when the installation angle of the inlet guide vane is small, the influence of the blade top clearance on the flow is small, but when the installation angle is large, the blade top clearance vortex is increased, and the flow loss is serious. Therefore, it is very necessary to improve the inlet guide vane tip structure and reduce the tip clearance of the inlet guide vane.
Disclosure of Invention
The invention provides a gas compressor inlet guide vane structure with brush seal, which aims to solve the problems that the influence of inlet guide vane gap leakage flow on main flow and the working efficiency of a gas compressor are reduced.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the utility model provides a take brush sealed compressor import stator structure, includes stator and seal structure, the one end that is close to the machine casket on the stator is provided with seal structure, seal structure includes brush silk, solid fixed ring and fixed plate, the brush silk sets up in the fixed ring, gu fixed ring passes through the fixed plate with the machine casket is fixed.
Further, the length of the brush wire is matched with the gap between the blade profile of the guide vane and the casing.
Further, the inner diameter of the fixing ring is matched with the outer diameter of the guide vane.
Further, the height of the brush wire is matched with the thickness between the guide vane and the casing.
Further, the guide vane is fixed to the casing by a guide vane rotating shaft and a center shaft.
The brush type sealing structure is additionally arranged at the gap between the guide vane and the casing, so that the flow control of the guide vane to the inlet is more accurate, the leakage can be effectively reduced, the inlet airflow is more uniform, and the influence of the leakage flow of the gap between the tops of the guide vane and the blade on the main flow is reduced, thereby improving the efficiency of the gas compressor and even the overall efficiency of the engine.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a three-dimensional view of the structure of the present invention;
FIG. 2 is an axial view of a brush seal inlet guide vane;
FIG. 3 is a schematic tip leakage flow diagram;
FIG. 4 is a radial view of the retaining ring;
FIG. 5 is a radially enlarged partial view of the retaining ring;
fig. 6 is a sectional view of the fixing ring.
In the figure, 1, a guide vane rotating shaft, 2, a casing, 3, brush wires, 4, a fixing ring, 5, a fixing plate, 6, a guide vane, 7 and a central shaft.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1-6, the inlet guide vane structure of the gas compressor with brush seal comprises a guide vane 6 and a seal structure, wherein the seal structure is arranged at one end of the guide vane 6 close to the casing, the seal structure comprises brush wires 3, a fixing ring 4 and a fixing plate 5, the brush wires 3 are arranged in the fixing ring 4, and the fixing ring 4 passes through the fixing plate 5 and the casing 2 is fixed. Further, the guide vane 6 is fixed to the casing 2 by the guide vane rotary shaft 1 and the central shaft 7. In this embodiment, it is preferable that the brush filaments 3 are flexible brush filaments, and the material of the brush filaments 3 is not required to withstand a severe environment with high temperature and high pressure, and therefore, a material that is relatively easy to process, such as an aluminum alloy, may be used. Because the gap is less, and the stator rotational frequency is not high, and this structure when the stator aperture changes, flexible brush silk can remain throughout and blade side contact, supports back row brush silk through quick-witted casket 2 end wall, and flexible brush silk can avoid bumping and grinding and lead to the permanent increase in seal gap between sealing member and the rotating parts. The depth of the inlet guide vane top penetrating into the groove is mainly changed according to the shape of the vane and the thickness of the casing 2, the height of the wire brushing ring can be adjusted to adapt, and the application range is wide. The hole depth is changed according to the inlet guide vane of the compressor, and the height of the brush wire ring is matched with the inlet guide vane of the compressor. The inlet guide vane is connected with a central shaft 7 and a casing through a guide vane rotating shaft 1, a brush wire bundle is fixed on the inner side of an open type brush wire fixing ring through a fusion welding process, and a brush wire fixing ring 4 is fixed with the end face of the casing 2 through a fixing plate 5 by welding. The fixing plate 5 not only plays a role of supporting the brush wires, but also plays a role of stabilizing the brush wire fixing ring.
Further, the length of the brush wire 3 matches with the gap between the blade profile of the guide vane 6 and the casing 2.
Further, the inner diameter of the fixing ring is matched with the outer diameter of the guide vane.
Further, the height of the brush wire 3 is matched with the thickness between the inlet guide vane 6 and the casing. In this embodiment, when the inlet channel guide vane rotates at a certain angle, in order to eliminate the interference between the guide vane and the casing 2 at the top end during rotation, a part of the front edge and the tail edge of the top of the guide vane is usually cut off, the top end of the guide vane has a certain gap with the casing 2, and the brush wire 3 and the brush wire fixing ring 4 of the brush seal structure are additionally arranged between the guide vane blade 6 and the casing 2, so that the air flow leaking from the top of the vane can be effectively reduced.
The guide vane top is generally arc-shaped, so that the guide vane top can rotate in cooperation with the wall surface of a casing, but gaps at the guide vane top are unevenly distributed, gaps at positions close to the middle rotating shaft of the guide vane top are small, and gaps between the front edge and the tail edge are large and form an arc shape. The blades are tapered along the radial direction, which causes the length of the brush wires 3 to decrease along with the increase of the blade height, and the specific value is determined by the blade profile. Because the inlet guide vane needs to adjust the opening and rotate, the maximum rotation angle reaches 90 degrees, a circle of brush tows 3 are arranged in the blade top gap to better seal when rotating, when the opening of the inlet guide vane is large, the blade top gap reduces the gap vortex at the maximum under various working conditions, and the stable operation working condition range of the compressor is enlarged. The blade top clearance of the guide blade can cause certain adverse effect on a flow field, a small part of air flow flows through the blade top clearance, the part of air flow can not be effectively adjusted, the adjusting capability of a main flow and the guide blade and the performance of the air compressor are badly affected, particularly, when the installation angle of the guide blade is 60 degrees, the flow can be increased by about 3 percent, the blade top clearance causes the air compressor to waste about 3 percent of air quantity during operation, the average about 3.7 percent of power is consumed, the efficiency of the air compressor is reduced by nearly 1 percent at the moment, the air leakage quantity is reduced through a brush type sealing structure, and the efficiency of the whole machine is improved.
The brush type sealing structure is simple and easy to process. The invention has no limit on the depth of the blade top to the groove and mainly changes according to the shape of the blade and the thickness of the casing, so the drilling depth is free and the application range is wide. The sealing structure is efficient in damping sealing, when the opening degree of the guide vane changes, the flexible brush wire of the brush type sealing can be always in contact with the side face of the blade, and the sealing structure has high sealing capacity. Because the contact surface of the brush seal and the rotating part is composed of metal wires with very small diameters, the brush wires play the role of countless small springs, and the permanent increase of the seal gap between the seal piece and the rotating part caused by long-time collision and abrasion with the rotating part is effectively avoided. The blade top clearance of stator can cause certain adverse effect to the flow field, and a small part of air current flows through from the blade top clearance, and this part air current can not effectively be adjusted, causes certain influence to mainstream and stator's regulating power and compressor's performance, and this brush seal structure has reduced the gas leakage volume, has improved complete machine efficiency.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (5)
1. The utility model provides a brush sealed compressor import stator structure, a serial communication port, including stator (6) and seal structure, the one end that is close to the machine casket on stator (6) is provided with seal structure, seal structure includes brush silk (3), solid fixed ring (4) and fixed plate (5), brush silk (3) set up in solid fixed ring (4), gu fixed ring (4) pass through fixed plate (5) with machine casket (2) are fixed.
2. The compressor inlet guide vane structure with brush seal according to claim 1, characterized in that the length of the brush wire (3) matches the gap between the profile of the guide vane (6) and the casing (2).
3. The compressor inlet guide vane structure with brush seal according to claim 1, characterized in that the inner diameter of the fixing ring (4) matches the outer diameter of the guide vane (6).
4. Compressor inlet guide vane structure with brush seal according to claim 1, characterized in that the brush filaments (3) have a height that matches the thickness between the guide vane (6) and the casing (2).
5. The compressor inlet guide vane structure with brush seal according to claim 1, characterized in that the guide vane (6) is fixed to the casing (2) by a guide vane rotating shaft (1) and a central shaft (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771396.XA CN113339323A (en) | 2021-07-07 | 2021-07-07 | Gas compressor inlet guide vane structure with brush seal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771396.XA CN113339323A (en) | 2021-07-07 | 2021-07-07 | Gas compressor inlet guide vane structure with brush seal |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113339323A true CN113339323A (en) | 2021-09-03 |
Family
ID=77483115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110771396.XA Pending CN113339323A (en) | 2021-07-07 | 2021-07-07 | Gas compressor inlet guide vane structure with brush seal |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113339323A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114109522A (en) * | 2021-11-29 | 2022-03-01 | 清华大学 | Guide vane structure for controlling clearance loss and power system |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6488471B1 (en) * | 2000-10-04 | 2002-12-03 | The United States Of America As Represented By The Secretary Of The Air Force | Gas-turbine brush seals with permanent radial gap |
| US6880829B1 (en) * | 2000-11-06 | 2005-04-19 | Advanced Components & Materials, Inc. | Compliant brush shroud assembly for gas turbine engine compressors |
| US20060088409A1 (en) * | 2004-10-21 | 2006-04-27 | General Electric Company | Grouped reaction nozzle tip shrouds with integrated seals |
| JP2011196280A (en) * | 2010-03-19 | 2011-10-06 | Mitsubishi Heavy Ind Ltd | Flow regulating device of rotary machine |
| CN105020160A (en) * | 2014-04-22 | 2015-11-04 | 南阳康派森流体设备科技股份有限公司 | Efficient flow adjusting device for compressor |
| CN105927588A (en) * | 2016-04-29 | 2016-09-07 | 沈阳透平机械股份有限公司 | Booster compressor inlet guide vane adjusting device and method |
| US20160290511A1 (en) * | 2013-11-19 | 2016-10-06 | Siemens Aktiengesellschaft | Shaft seal and method for producing same |
| CN112343854A (en) * | 2020-11-05 | 2021-02-09 | 中国科学院工程热物理研究所 | Adjustable blade sealing structure |
-
2021
- 2021-07-07 CN CN202110771396.XA patent/CN113339323A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6488471B1 (en) * | 2000-10-04 | 2002-12-03 | The United States Of America As Represented By The Secretary Of The Air Force | Gas-turbine brush seals with permanent radial gap |
| US6880829B1 (en) * | 2000-11-06 | 2005-04-19 | Advanced Components & Materials, Inc. | Compliant brush shroud assembly for gas turbine engine compressors |
| US20060088409A1 (en) * | 2004-10-21 | 2006-04-27 | General Electric Company | Grouped reaction nozzle tip shrouds with integrated seals |
| JP2011196280A (en) * | 2010-03-19 | 2011-10-06 | Mitsubishi Heavy Ind Ltd | Flow regulating device of rotary machine |
| US20160290511A1 (en) * | 2013-11-19 | 2016-10-06 | Siemens Aktiengesellschaft | Shaft seal and method for producing same |
| CN105020160A (en) * | 2014-04-22 | 2015-11-04 | 南阳康派森流体设备科技股份有限公司 | Efficient flow adjusting device for compressor |
| CN105927588A (en) * | 2016-04-29 | 2016-09-07 | 沈阳透平机械股份有限公司 | Booster compressor inlet guide vane adjusting device and method |
| CN112343854A (en) * | 2020-11-05 | 2021-02-09 | 中国科学院工程热物理研究所 | Adjustable blade sealing structure |
Non-Patent Citations (1)
| Title |
|---|
| （英）理查德·布洛克利（RICHARD BLOCKLEY） 等主编，毛军逵等译: "《航空航天科技出版工程.2.推进与动力》", 30 June 2016, 北京理工大学出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114109522A (en) * | 2021-11-29 | 2022-03-01 | 清华大学 | Guide vane structure for controlling clearance loss and power system |
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| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210903 |